Abstract: An auxiliary flaperon control is pivotally mounted on the trailing edge of each wing of an aircraft between the outboard control surfaces and the fuselage and in close proximity to the tail of said aircraft; the auxiliary flaperon controls being operable relative to the outboard control surfaces to induce supplementary aerodynamic forces on the aircraft tail to thereby augment the effectiveness of aircraft lateral and directional control.

Abstract: A folding airfoil for an aircraft in which the wing or stabilizer airfoil n be folded and contained entirely within the fuselage of the aircraft. The airfoil comprises a series of elongated sheet metal channel sections of generally C-shaped cross section with the cross sectional dimension of successive channels decreasing so that each can nest entirely within an adjacent channel. The channels are each pivotally connected at the root end to the aircraft fuselage structure at spaced intervals along the chord line of the extended airfoil and the end sections of the channels are pivotally connected to each other such that the channels are pivotable between (1) an extended position extending spanwise of the extended airfoil to lie in tandem one behind the other, with adjacent channels partially overlapping and (2) a retracted or folded position in which the channels are nested within the leading edge channel section and lie along the chord line of the extended airfoil along the line of channel root end pivotal connections.

Abstract: An aircraft seating arrangement for an aircraft in which the seats for the pilot and passengers are disposed on first and second pairs of longitudinally extending rails in a fashion that permits the seated occupant to position his seat at a desired location along the fuselage of the aircraft. The rails or tracks are disposed in the floor of the fuselage and roller members cooperate with the parallel tracks and with the seat frames to facilitate sliding the seats back and forth along the rails or tracks. A suitable detent is provided for locking the seat with respect to the rails at the desired location. Also, provision is made for rotating the seat cushion assembly from a normal, horizontal orientation to a substantially vertical orientation when a latching device is released.

Abstract: A plurality of passageways, each having its longitudinal axis substantially parallel to the flight path of an aircraft, extend through the wings, fuselage, horizontal elevators, and rudder for the purpose of permitting air to pass through these areas. The passageways diverge from front to rear on either side of the longitudinal axis. The front openings leading into the passageways are of such size and so spaced as to exhibit considerable reduction in parasite drag generated at the leading edges of the wings, elevators, and rudder, as well as at the front end of the fuselage.

Abstract: An aircraft in which the fuselage and wings are configured in a blended wing design has a door opening in the fuselage adjacent the wing and a door assembly for closing the door opening. The door assembly includes a door having an exterior panel that conforms to the shape of the aircraft at the location of the door opening when the door is closed and having an interior structure configured in a series of steps. The door is movable between a closed position in which an upper edge of the door panel is adjacent an upper edge of the door opening and an open position in which the door panel lies substantially within the wing and in which the upper edge of the door panel is adjacent an upper surface of the wing and spaced from the fuselage. When the door is in the open position, the steps form a stairway leading from the fuselage up and out of the aircraft to the upper surface of the wing. Preferably, the door assembly also includes a movable wing panel which is slaved to the door such that, as the door is moved from the closed to the open position, the wing panel moves to uncover an opening in the wing upper surface through which the door passes to reach its open position.

Abstract: The present canard type of aircraft comprises steering rudder elements which are tiltable substantially about the leading edge of each wing of the aircraft, whereby the respective edge of the rudder element extends alongside said leading edge of the respective wing. Another edge of the rudder element extends alongside a surface portion of the fuselage or body of the aircraft in close conformity with said surface portion, but movable relative thereto. A sealing may be inserted between the rudder element and the fuselage in such a manner that said movement is permitted.

Abstract: Theme I the context of airborne-noise transmission through an aircraft fuselage, a mathematical model is presented for sound transmission into a stiffened cylindrical shell. The stiffening effect of the ring frames and stringers is approximated by a "smeared" stiffener theory which includes the eccentricity of the stiffeners. Numerical results are presented for a typical narrow-bodied jet in cruising flight.

Abstract: A combination air brake and engine shield for a jet powered aircraft. A hydraulically operated, hinged shield member, shaped so as to conform to the surface of the aircraft fuselage when in its retracted position, may be swung outwardly therefrom so as to be disposed in front of the air intake of the jet engine powering the craft, to thereby divert any foreign objects from being drawn into the intake and damaging the engine. The same arrangement may also serve as an air brake to effect deceleration of the aircraft. Spring loaded louvers are provided in the shield to permit sufficient air to reach the engine such that problems due to cavitation are avoided.

Abstract: An analytical study was performed to determine the best structural approach for design of primary wing and fuselage structure of a Mach 2.7 arrow wing supersonic cruise aircraft. Concepts were evaluated considering near term start of design. Emphasis was placed on the complex interactions between thermal stress, static aeroelasticity, flutter, fatigue and fail safe design, static and dynamic loads, and the effects of variations in structural arrangements, concepts and materials on these interactions. Results indicate that a hybrid wing structure incorporating low profile convex beaded and honeycomb sandwich surface panels of titanium alloy 6Al-4V were the most efficient. The substructure includes titanium alloy spar caps reinforced with boron polyimide composites. The fuselage shell consists of hat stiffened skin and frame construction of titanium alloy 6Al-4V. A summary of the study effort is presented, and a discussion of the overall logic, design philosophy and interaction between the analytical methods for supersonic cruise aircraft design are included.

Abstract: The stowable airfoil structure is a tapered, high aspect ratio, retractable and foldable wing for aircraft which provides minimum aerodynamic drag during launch and minimum space for ground storage. The airfoil utilizes a forward leading edge box section to which is attached a plurality of spanwise channels hinged together for movement in a chordwise direction. Retraction of these elements takes place by the utilization of suitable actuators so as to move the hinged elements forwardly in a nested position thereby substantially reducing the width of the wing or airfoil which is then folded to lie along side the fuselage of an aircraft.

Abstract: Thrust reverser for a jet engine of an aircraft, comprising two symmetrical doors mounted to pivot about an axis which is transverse and substantially diametrical with respect to the jet of the engine and which is disposed downstream of the jet exhaust pipe thereof, the doors being adapted to occupy a folded or stowed position in which they form part of the fairing of the engine or fuselage of the aircraft, or an unfolded or opened out position for which they are disposed transversely with respect to the jet. According to the invention, each of the doors is formed by a single skin which is at least substantially hemi-truncated in shape.

Abstract: An aircraft has a fuselage with a forward cockpit, an aft mounted fin, and an upper deck extending between the two, there being a weapon launcher assembly of elongated form with a forward end through which rocket propelled weapons are launched, a rearward end through which rocket exhaust is dissipated, and an upper deck extending between the two, the launcher being pivotable between a stowed position wherein it lies with its upper deck smoothly continuous with the upper deck of the fuselage and an extended weapon launch position wherein the weapons can be launched clear of the forward cockpit.

Abstract: A flying device capable of carrying man, which contains a wing, a fuselage, and means such as cables for attaching the wing to the fuselage so that the fuselage is suspended below the wing. The fuselage contains a propulsion unit and normally does not have wings for creating a lifting force as in ordinary aircraft.

Abstract: A powered aircraft having an auxiliary thruster engine normally disposed within the fuselage of the aircraft, but which, when activated, is moved to an operative position outside of the fuselage prior to its energization, the auxiliary thruster engine providing sufficient thrust to power the aircraft if one or more of its normal engines is inactive.

Abstract: Laser altimeter/profilometer apparatus utilizing a CW CO 2 laser transmitter mounted on an aircraft so as to transmit a narrow laser beam towards the terrain below the aircraft. The scattered laser signals are received in a receiver mounted on the aircraft, some distance along the fuselage from the transmitter, and the doppler shift in frequency of the received signal is determined. That doppler shifted frequency is utilized to calculate the altitude of the aircraft above the ground over which it is flying.

Abstract: A theoretical method is presented for predicting the lateral-directional stability derivatives of wing-body combinations with or without the blowing jet effect The fuselage effect is accounted for by the axial distribution of vortex multiplets Comparison of the predicted results with experiments and other theoretical methods show good agreement for configurations without the blowing jet More applicable experimental data with blowing jets are needed to establish the accuracy of the theory

Abstract: A quasisteady analysis of the aeroelastic stability of the lateral (antisymmetric) modes of the 747/Orbiter vehicle demonstrates that the interference effect of the Orbiter wake on the 747 tail furnishes an aerodynamic undamping contribution to the low-frequency elastic modes. Likewise, the upstream influence of the 747 tail and aft fuselage on the Orbiter beavertail tail fairing also is undamping. Fortunately, these undamping effects cannot overpower the large damping contribution of the 747 tail, and the yaw modes are damped for the configurations analyzed.

Abstract: A vertical takeoff and landing aircraft having a tail assembly supporting structure which is pivotally connected to the fuselage, and having a shrouded fan driven by an engine submerged in the fuselage, the shrouded fan being connected to and rotatable with the tail supporting structure so as to direct the slipstream of the shrouded fan over the tail assembly at all times.

Abstract: A folding assembled article in the form of a toy airplane has a fuselage of paper folded along a longitudinal line and a paper wing assembled with the fuselage and movable between a folded configuration, wherein the assembly is flat for packaging purposes, and an erect configuration, wherein the wing is maintained in an extended lateral position relative to the fuselage for flight.

Abstract: An investigation was conducted in the Langley 8-foot transonic pressure tunnel on two aspect-ratio 11.95 supercritical wings that were tested in combination with a representative wide-body-type fuselage. The two supercritical wings have identical planforms for equal sweep angles and differ only in thickness. Each wing was tested at quarter-chord sweep angles of 27 deg and 30 deg. At the higher sweep angle, the aspect ratio is reduced to 11.36. At 27 deg of quarter-chord sweep, the thicker supercritical wing (SCW-1) has maximum streamwise thickness-to-chord ratios of 0.16 at the wing-fuselage juncture, 0.14 at the planform break station, and 0.12 at the tip. The thinner wing (SCW-2) has maximum streamwise thickness-to-chord ratios of 0.144, 0.12, and 0.10 at the same stations respectively. Tests were also conducted on the thinner supercritical wing at the 27 deg sweep angle with a 15.24 cm (6.0 in.) shorter span which results in an aspect ratio of 10.25. For comparison, data were obtained on a current wide-body transport wing (AR=7) that was tested on the same fuselage used with the supercritical wings.

Abstract: This paper describes experimental and analytical studies of the interior noise of twin-engine, propeller-driven, light aircraft Experimental results indicate that interior noise levels due to propeller noise can be reduced by reduction of engine rpm at constant airspeed (about 3 dB), by synchronization of the twin engines/propellers (up to 12 dB), and by increasing the distances from propeller tip to fuselage The analytical model described uses modal methods and incorporates the flat-sided geometrical and skin-stringer structural features of light aircraft Initial results show good agreement with measured noise transmitted into a rectangular box through a flat panel

Abstract: Current design philosophy for scramjet-powered hypersonic aircraft results in configurations with the entire lower fuselage surface utilized as part of the propulsion system. The lower aft-end of the vehicle acts as a high expansion ratio nozzle. Not only must the external nozzle be designed to extract the maximum possible thrust force from the high energy flow at the combustor exit, but the forces produced by the nozzle must be aligned such that they do not unduly affect aerodynamic balance. The strong coupling between the propulsion system and aerodynamics of the aircraft makes imperative at least a partial simulation of the inlet, exhaust, and external flows of the hydrogen-burning scramjet in conventional facilities for both nozzle formulation and aerodynamic-force data acquisition. Aerodynamic testing methods offer no contemporary approach for such vehicle design requirements. NASA-Langley has pursued an extensive scramjet/airframe integration R&D program for several years and has recently developed a promising technique for simulation of the scramjet exhaust flow for hypersonic aircraft. Current results of the research program to develop a scramjet flow simulation technique through the use of substitute gas blends are described in this paper.

Abstract: A preliminary assessment of possible means for improving the low speed aerodynamic characteristics of advanced supersonic cruise arrow wing configurations and to extend the existing data base of such configurations has been made. Principle configuration variables included wing-leading and trailing-edge flap deflection, fuselage nose strakes, and engine exhaust nozzle deflection. Results showed that deflecting the wing leading edge apex flaps downward provided improved longitudinal stability but resulted in reduced directional stability. The model exhibited relatively low values of directional stability over the operational angle of attack range and experienced large asymmetric yawing moments at high angles of attack. The use of nose strakes was found to be effective in increasing the directional stability and eliminating the asymmetric yawing moment.

Abstract: : A method is described for calculating the complete pressure distribution on a body with separated flow. The boundary layer characteristics are calculated along several streamlines up to the point where separation is predicted. The separated flow is modeled by streamwise panels of uniform vorticity attached to the body near the predicted separation line. Comparisons are presented of calculated and experimental pressure distributions for a cylinder, a sphere and the BO105 fuselage. The results are in fair agreement, but there are certain features of the results and restrictions of the source/vortex inviscid model which need improvement. (Author)

Abstract: A computer program, GEMPAK, has been developed to aid in the generation of detailed configuration geometry. The program was written to allow the user as much flexibility as possible in his choices of configurations and the detail of description desired and at the same time keep input requirements and program turnaround and cost to a minimum. The program consists of routines that generate fuselage and planar-surface (winglike) geometry and a routine that will determine the true intersection of all components with the fuselage. This paper describes the methods by which the various geometries are generated and provides input description with sample input and output. Also included are descriptions of the primary program variables and functions performed by the various routines. The FORTRAN program GEMPAK has been used extensively in conjunction with interfaces to several aerodynamic and plotting computer programs and has proven to be an effective aid in the preliminary design phase of aircraft configurations.

Abstract: A lightweight, segmented, easily assembled aircraft having a hollow fuselage tube, upon which the cockpit, wing, empennage, landing gear, engine, and shell segments are supported and secured, is presented. The wing construction aerodynamically extends the effective wingspan of the aircraft and stabilizes flight by including an aileron slot, which rams positive pressured air from the lower surface of the wing over the upper surface of the wing to laminarize the turbulent air near the ailerons, and including an end plate, which is toed-in and canted towards the upper surface. A fore shell segment separates from and moves fowardly of a fixed, aft shell segment along a track apparatus, secured to the hollow fuselage tube, to permit access to the cockpit of the aircraft.

Abstract: : The space-time integral equation approach is extended to the problem of simple aircraft shapes. The target consisted of a cylindrical fuselage, and rectangular wings, stabilizers, and rudder. Calculations were compared to measurements. The inverse scattering problem was reformulated to take advantage of direct time domain method of solution. Solutions for the sphere, sphere capped cylinder, and flat end cylinder were developed. (Author)

Abstract: The external pallets are loaded on the aircraft as semi integrated system. A wide range of additional, for example, military equipment can be accommodated on or within the aircraft without increasing air resistance. The fuselage underside (2) and the fuselage side walls have mounting rails (15, 16) in the form of T slots parallel to aircraft longitudinal axis. The mounting rails receive support profiles (1) of the load carriers such as a support pallet (10) for bombs (13). An attached housing can have hinged, downwards opening doors. The doors are actuated by the energy from the aircraft power plant.